Fuel cell system control method and device, storage medium and electronic equipment

Abstract

The invention relates to the field of aircrafts, in particular to a fuel cell system control method and device, a storage medium and electronic equipment. The fuel cell system control method comprises the following steps: acquiring flight parameters of an aircraft, wherein the flight parameters comprise the flight altitude of the aircraft; determining a target flight condition of the aircraft according to the flight parameters; calculating electric pile required power of a fuel cell system of the aircraft under the target flight working condition; and controlling the fuel cell system to provide power support for the aircraft based on the stack demand power. Through the method, the fuel cell system of the aircraft can better adapt to power requirements under different flight working conditions, and can provide stable and sufficient power support for the aircraft, so that the performance stability and reliability of the aircraft are improved.

Description

Technical Field

[0001] The present disclosure relates to the field of aircraft, and in particular to a fuel cell system control method, device, storage medium and electronic equipment. Background Art

[0002] With the rapid development and widespread application of aircraft technology, the performance stability and reliability of aircraft in various complex environments have become the focus of research. In various complex environments, the power supply system of aircraft faces huge challenges. Traditional battery power supply methods often cannot meet the continuous and stable power supply needs of aircraft under these extreme conditions.

[0003] Fuel cells are an efficient and environmentally friendly energy supply method that can continuously convert chemical energy into electrical energy. However, the performance of the fuel cell system is affected by its working environment and operating conditions, thus affecting the power supply of the aircraft. Summary of the invention

[0004] The main purpose of the present disclosure is to provide a fuel cell system control method, device, storage medium and electronic equipment, aiming to solve the technical problem in the prior art that the performance of the fuel cell system is affected by the working environment and operating conditions, thereby affecting the power supply of the aircraft.

[0005] To achieve the above objectives, the present disclosure provides a fuel cell system control method, comprising:

[0006] Acquiring flight parameters of an aircraft, wherein the flight parameters include a flight altitude of the aircraft;

[0007] Determining a target flight condition of the aircraft according to the flight parameters;

[0008] Calculating the required power of the fuel cell stack of the fuel cell system of the aircraft under the target flight condition;

[0009] Based on the power demand of the fuel cell stack, the fuel cell system is controlled to provide power support for the aircraft.

[0010] Optionally, the calculating the stack power requirement of the fuel cell system of the aircraft under the target flight condition includes:

[0011] calculating the air flow demand of the air compressor of the fuel cell system under the target flight condition; determining the required air compressor power of the air compressor of the fuel cell system under the target flight condition according to the air flow demand;

[0012] The required power of the fuel cell stack of the fuel cell system under the target flight condition is calculated based on the required power of the air compressor.

[0013] Optionally, calculating the required power of the fuel cell stack of the fuel cell system under the target flight condition according to the required power of the air compressor includes:

[0014] If the target flight condition is a climbing condition, the required power of the first stack of the fuel cell system under the climbing condition is calculated according to the following calculation formula:

[0015] P stack1 =P air1 +P aff

[0016] Among them, P stack1 is the power required by the first stack, P air1 is the required power of the air compressor, P aff The power requirements of other auxiliary components of the fuel cell system;

[0017] If the target flight condition is a high-altitude level flight condition, the required power of the second stack of the fuel cell system under the high-altitude level flight condition is calculated according to the following calculation formula:

[0018] P stack2 =P air1 +P aff -ΔP

[0019] Among them, P stack2 is the power demand of the second stack, and ΔP is the increase in the stack power of the fuel cell system when the air flow rate increases; or

[0020] If the target flight condition is a landing condition, the required power of the third stack of the fuel cell system under the landing condition is calculated according to the following calculation formula:

[0021] P stack3 =P air1 +P aff

[0022] Among them, P stack3 Power is required for the third fuel cell stack.

[0023] Optionally, calculating the required power of the fuel cell stack of the fuel cell system under the target flight condition according to the required power of the air compressor includes:

[0024] According to the calculation formula, the improvement value of the stack power of the fuel cell system is calculated:

[0025] ΔP=P2-P1

[0026] Wherein, P1 is the first required power of the fuel cell system when the flight altitude is not considered, and P2 is the second required power of the fuel cell system when the altitude is considered.

[0027] Optionally, determining the required air compressor power of the air compressor of the fuel cell system under the target flight condition according to the air flow requirement includes:

[0028] The required power of the air compressor is calculated by the following formula:

[0029] P air1 =Q1P a k3 / η

[0030] Among them, P air1 is the required power of the air compressor, Q1 is the air flow requirement, P a is the working pressure of the air compressor, k3 is a constant, and η is the energy conversion efficiency of the air compressor.

[0031] Optionally, the calculating the air flow demand of the air compressor of the fuel cell system under the target flight condition includes:

[0032] determining an initial air flow requirement, wherein the initial air flow requirement is an air flow requirement of the fuel cell system under the target flight condition without considering a change in oxygen concentration;

[0033] Acquire a first change relationship, where the first change relationship is used to characterize a change relationship between oxygen content and flight altitude;

[0034] Calculating the air flow demand according to the initial air flow demand and the first change relationship;

[0035] The air flow requirement is calculated according to the following formula:

[0036]

[0037] Wherein, Q1 is the air flow demand, k2 is a constant, and H is the flight altitude corresponding to the target flight condition.

[0038] Optionally, determining the initial air flow requirement includes:

[0039] Obtaining a first relationship between the air flow demand of the fuel cell system and the air compressor speed of the air compressor;

[0040] Obtaining a second relationship between the air compressor speed and the flight altitude;

[0041] Determining a third relationship between the air flow requirement of the fuel cell system and the flight altitude according to the first relationship and the second relationship;

[0042] Calculating the initial air flow requirement according to the third relationship;

[0043] The initial air flow requirement is calculated by using the following formula:

[0044] Q0=k0k1H

[0045] Wherein, Q0 is the initial air flow requirement, k0 and k1 are both constants, and H is the flight altitude corresponding to the target flight condition.

[0046] Optionally, obtaining the first change relationship includes:

[0047] Collect oxygen content corresponding to different flight altitudes;

[0048] Performing curve fitting on the different flight altitudes and the oxygen contents corresponding to the different flight altitudes to obtain the first variation relationship;

[0049] The first change relationship can be expressed by the following exponential relationship:

[0050] O2=O′2*e -k H0

[0051] Among them, O2 is the oxygen content relative to sea level, O2′ is the oxygen content at sea level, k is a constant, and H0 is the flight altitude.

[0052] In addition, to achieve the above-mentioned purpose, the present disclosure also provides a fuel cell system control device, including:

[0053] An acquisition module, used to acquire flight parameters of the aircraft, wherein the flight parameters include the flight altitude of the aircraft;

[0054] A determination module, used to determine a target flight condition of the aircraft according to the flight parameters;

[0055] A calculation module, used to calculate the required power of the fuel cell stack of the fuel cell system of the aircraft under the target flight condition;

[0056] A control module is used to control the fuel cell system to provide power support for the aircraft based on the power demand of the fuel cell stack.

[0057] In addition, to achieve the above objectives, the present disclosure also provides a computer-readable storage medium, on which a computer program is stored, and a processor executes the computer program to implement the above method.

[0058] In addition, to achieve the above-mentioned purpose, the present disclosure also provides an electronic device, which includes a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the above-mentioned method.

[0059] In addition, to achieve the above objectives, the present disclosure also provides a computer program product, which implements the above method when executed by a processor.

[0060] The fuel cell system control method, device, storage medium and electronic device proposed in the embodiment of the present disclosure first obtain the flight parameters of the aircraft during the flight, then determine the target flight conditions of the aircraft based on the flight parameters, then calculate the stack power required by the fuel cell system of the aircraft under the target flight conditions, and finally control the fuel cell system to provide power support for the aircraft based on the stack power required. In this way, the current flight condition of the aircraft can be judged according to the flight parameters of the aircraft obtained in real time, and then the stack power required by the fuel cell system under the condition can be predicted and calculated, and then the working state of the fuel cell is adjusted according to the calculated stack power required to ensure that stable and sufficient power support is provided for the aircraft. Through this method, the aircraft fuel cell system can better adapt to the power demand under different flight conditions, especially under extreme conditions such as high altitude areas and rapid climb / landing, and can still provide stable and sufficient power support for the aircraft, thereby improving the performance stability and reliability of the aircraft and avoiding the waste of system power. BRIEF DESCRIPTION OF THE DRAWINGS

[0061] In order to more clearly illustrate the embodiments of the present disclosure or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0062] Figure 1 A schematic diagram of the device structure of the hardware operating environment involved in the embodiment of the present disclosure;

[0063] Figure 2 A schematic diagram of the structure of a fuel cell system involved in the embodiment of the present disclosure;

[0064] Figure 3 A schematic flow chart of a fuel cell system control method according to an embodiment of the present disclosure;

[0065] Figure 4A schematic diagram of the change in the required air flow of an air compressor with the altitude involved in the embodiment of the present disclosure;

[0066] Figure 5 A schematic diagram of the change of oxygen content with altitude involved in an embodiment of the present disclosure;

[0067] Figure 6 A schematic diagram showing the change in power of an air compressor according to an embodiment of the present disclosure with respect to altitude;

[0068] Figure 7 A schematic diagram of a system power demand change in different flight conditions involved in an embodiment of the present disclosure;

[0069] Figure 8 A schematic diagram of a stack power variation with load and air flow rate involved in an embodiment of the present disclosure;

[0070] Fig. 9 This is a structural block diagram of a fuel cell system control device involved in an embodiment of the present disclosure.

[0071] The realization of the objectives, functional features and advantages of the present disclosure will be further described in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0072] The following will be combined with the drawings in the embodiments of the present disclosure to clearly and completely describe the technical solutions in the embodiments of the present disclosure. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all the embodiments. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present disclosure.

[0073] Reference Figure 1 , Figure 1 The figure is a schematic diagram of the device structure of the hardware operating environment involved in the embodiment of the present disclosure.

[0074] Typically, the device includes: at least one processor 301, a memory 302, and a fuel cell system control program stored in the memory 302 and executable on the processor 301, wherein the fuel cell system control program is configured to implement the steps of the fuel cell system control method as described above.

[0075] The processor 301 may include one or more processing cores, such as a 4-core processor, an 8-core processor, etc. The processor 301 may be implemented in at least one hardware form of DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), and PLA (Programmable Logic Array). The processor 301 may also include a main processor and a coprocessor. The main processor is a processor for processing data in the awake state, also known as a CPU (Central Processing Unit); the coprocessor is a low-power processor for processing data in the standby state. In some embodiments, the processor 301 may be integrated with a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content to be displayed on the display screen. The processor 301 may also include an AI (Artificial Intelligence) processor, which is used to process operations related to the fuel cell system control method, so that the fuel cell system control method model can be trained and learned autonomously to improve efficiency and accuracy.

[0076] The memory 302 may include one or more storage media, which may be non-transitory. The memory 302 may also include a high-speed random access memory, and a non-volatile memory, such as one or more disk storage devices, flash memory storage devices. In some embodiments, the non-transitory storage medium in the memory 302 is used to store at least one instruction, which is used to be executed by the processor 301 to implement the fuel cell system control method provided in the method embodiment of the present disclosure.

[0077] In some embodiments, the terminal may further include: a communication interface 303 and at least one peripheral device. The processor 301, the memory 302 and the communication interface 303 may be connected via a bus or a signal line. Each peripheral device may be connected to the communication interface 303 via a bus, a signal line or a circuit board. Specifically, the peripheral device includes: at least one of a radio frequency circuit 304, a display screen 305 and a power supply 306.

[0078] The communication interface 303 may be used to connect at least one peripheral device related to I / O (Input / Output) to the processor 301 and the memory 302. In some embodiments, the processor 301, the memory 302, and the communication interface 303 are integrated on the same chip or circuit board; in some other embodiments, any one or two of the processor 301, the memory 302, and the communication interface 303 may be implemented on a separate chip or circuit board, which is not limited in this embodiment.

[0079] The radio frequency circuit 304 is used to receive and transmit RF (Radio Frequency) signals, also known as electromagnetic signals. The radio frequency circuit 304 communicates with the communication network and other communication devices through electromagnetic signals. The radio frequency circuit 304 converts electrical signals into electromagnetic signals for transmission, or converts received electromagnetic signals into electrical signals. Optionally, the radio frequency circuit 304 includes: an antenna system, an RF transceiver, one or more amplifiers, a tuner, an oscillator, a digital signal processor, a codec chipset, a user identity module card, and the like. The radio frequency circuit 304 can communicate with other terminals through at least one wireless communication protocol. The wireless communication protocol includes, but is not limited to: a metropolitan area network, various generations of mobile communication networks (2G, 3G, 4G and 5G), a wireless local area network and / or a WiFi (Wireless Fidelity) network. In some embodiments, the radio frequency circuit 304 may also include circuits related to NFC (Near Field Communication), which is not limited in the present disclosure.

[0080] The display screen 305 is used to display the UI (User Interface). The UI may include graphics, text, icons, videos, and any combination thereof. When the display screen 305 is a touch display screen, the display screen 305 also has the ability to collect touch signals on the surface or above the surface of the display screen 305. The touch signal can be input to the processor 301 as a control signal for processing. At this time, the display screen 305 can also be used to provide virtual buttons and / or virtual keyboards, also known as soft buttons and / or soft keyboards. In some embodiments, the display screen 305 can be one, the front panel of the electronic device; in other embodiments, the display screen 305 can be at least two, respectively arranged on different surfaces of the electronic device or in a folding design; in some embodiments, the display screen 305 can be a flexible display screen, arranged on a curved surface or a folding surface of the electronic device. Even, the display screen 305 can also be set to a non-rectangular irregular shape, that is, a special-shaped screen. The display screen 305 can be made of materials such as LCD (Liquid Crystal Display), OLED (Organic Light-Emitting Diode, organic light-emitting diode).

[0081] The power supply 306 is used to power various components in the electronic device. The power supply 306 can be AC ​​power, DC power, a disposable battery, or a rechargeable battery. When the power supply 306 includes a rechargeable battery, the rechargeable battery can support wired charging or wireless charging. The rechargeable battery can also be used to support fast charging technology. Those skilled in the art will understand that Figure 1 The structure shown in the figure does not constitute a limitation of the device, and may include more or less components than shown in the figure, or combine certain components, or arrange the components differently.

[0082] In addition, the embodiment of the present disclosure further proposes a storage medium, on which a fuel cell system control program is stored, and when the fuel cell system control program is executed by a processor, the steps of the fuel cell system control method described above are implemented. Therefore, it will not be repeated here. In addition, the description of the beneficial effects of adopting the same method will not be repeated. For technical details not disclosed in the storage medium embodiment involved in the present disclosure, please refer to the description of the method embodiment of the present disclosure. As an example, program instructions can be deployed to be executed on one device, or on multiple devices located at one location, or on multiple devices distributed at multiple locations and interconnected by a communication network.

[0083] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be implemented by instructing related hardware through a computer program, and the above-mentioned program can be stored in a storage medium, and when the program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, the above-mentioned storage medium can be a disk, an optical disk, a read-only memory (ROM) or a random access memory (RAM), etc.

[0084] In related technologies, the air flow demand of automotive fuel cells is mainly adjusted with load changes. When the fuel cell system of an aircraft flies at different altitudes, it faces not only load changes, but also changes in oxygen concentration. This change will directly affect the air flow demand of the system, and then change the speed requirement of the air compressor in the fuel cell system. If the influence of altitude factors is ignored, the fuel cell system may not be able to provide sufficient power support for the aircraft.

[0085] Even when the load remains constant, an increase in air flow will have a slight effect on the output power of the fuel cell. If this phenomenon is ignored in actual system control, it may not only lead to power waste, but also reduce the overall efficiency of the system.

[0086] In view of this, the present disclosure proposes a fuel cell system control method, device, storage medium and electronic equipment aircraft, which fully consider the actual factors under different flight conditions, such as changes in oxygen concentration caused by altitude, etc., to ensure that the system supply can accurately match the power requirements of the aircraft under various flight conditions.

[0087] Figure 2 FIG. 1 is a schematic diagram of a fuel cell system structure involved in the embodiment of the present disclosure. Figure 2 As shown, the fuel cell system includes an electrical subsystem, a thermal management subsystem, a hydrogen subsystem, and an air subsystem. In the air subsystem, auxiliary components such as the air compressor are powered by the fuel cell stack. As the flight altitude of the aircraft changes, changes in the oxygen content in the air will cause changes in the air flow demand of the fuel cell, thereby changing the required power of the air compressor. Therefore, the present disclosure focuses on the power matching problem between the fuel cell stack and the air compressor, and proposes a fuel cell system control method that is applied to Figure 2 The fuel cell system shown.

[0088] Reference Figure 3 , Figure 3 The present invention is a flowchart of a fuel cell system control method according to an embodiment of the present invention, which includes the following steps:

[0089] Step S11: Acquire the flight parameters of the aircraft, where the flight parameters include the flight altitude of the aircraft.

[0090] Step S12: Determine the target flight condition of the aircraft according to the flight parameters.

[0091] Step S13: Calculate the stack power requirement of the fuel cell system of the aircraft under the target flight condition.

[0092] Step S14: Based on the power demand of the fuel cell stack, control the fuel cell system to provide power support for the aircraft.

[0093] For example, the flight parameters may include the flight altitude, and may also include one or more of the flight speed, the operation of the throttle and the joystick, and the display of the horizon, which are not specifically limited in the embodiments of the present disclosure. Correspondingly, the target flight condition of the aircraft may be determined according to one or more of the change in the flight altitude, the change in the flight speed, the operation of the throttle and the joystick, and the display of the horizon within a preset time period.

[0094] The determination criteria for each flight condition can be set and adjusted according to different aircraft and / or different flight environments and flight missions, and the present disclosure embodiment does not limit this. The present disclosure embodiment will not repeat the specific method for determining the target flight condition of the aircraft.

[0095] Through the above technical solution, the flight parameters of the aircraft during flight are first obtained, and then the target flight conditions of the aircraft are determined according to the flight parameters, and then the stack power required by the fuel cell system of the aircraft under the target flight conditions is calculated, and finally based on the stack power required, the fuel cell system is controlled to provide power support for the aircraft. In this way, the current flight condition of the aircraft can be judged according to the flight parameters of the aircraft obtained in real time, and then the stack power required by the fuel cell system under the condition can be predicted and calculated, and then the working state of the fuel cell is adjusted according to the calculated stack power required to ensure that stable and sufficient power support is provided for the aircraft. Through this method, the aircraft fuel cell system can better adapt to the power demand under different flight conditions, especially under extreme conditions such as high altitude areas and rapid climb / landing, and can still provide stable and sufficient power support for the aircraft, thereby improving the performance stability and reliability of the aircraft and avoiding the waste of system power.

[0096] In a possible manner, calculating the stack power requirement of the fuel cell system of the aircraft under the target flight condition includes:

[0097] Calculate the air flow requirements of the fuel cell system's air compressor under target flight conditions;

[0098] Determine the required power of the air compressor of the fuel cell system under the target flight conditions according to the air flow demand;

[0099] Based on the required power of the air compressor, calculate the required power of the fuel cell system stack under the target flight conditions.

[0100] For example, the operation of the fuel cell system depends on the amount of air that reacts with hydrogen to generate electricity. The air flow requirement is affected by several key factors, including the fuel cell stack power, stack efficiency, and reaction stoichiometric ratio. Given the specificity of flight conditions, these parameters may vary, so it is crucial to accurately calculate the air flow requirement that matches the conditions.

[0101] Secondly, in order to meet the air flow demand of the fuel cell system, it is usually achieved with the help of an air compressor. The power demand of the air compressor is not fixed, but changes dynamically based on the required air flow, the efficiency of the air compressor, and other relevant parameters of the system. Based on the previously calculated air flow demand, the power required by the air compressor under specific flight conditions can be accurately estimated.

[0102] Finally, based on the power demand of the air compressor under specific operating conditions, the required stack power of the fuel cell system to meet the target flight conditions can be further derived. This calculation process not only ensures the stable operation of the system, but also provides a scientific basis for optimizing the performance of the fuel cell system.

[0103] In a possible manner, the air flow demand of the air compressor of the fuel cell system under the target flight condition is calculated, including:

[0104] Determine an initial air flow requirement, where the initial air flow requirement is the air flow requirement of the fuel cell system under target flight conditions without considering changes in oxygen concentration;

[0105] Acquire a first change relationship, where the first change relationship is used to characterize a change relationship between oxygen content and flight altitude;

[0106] Calculating the air flow demand according to the initial air flow demand and the first change relationship;

[0107] Calculate the air flow requirement by using the following calculation:

[0108]

[0109] Among them, Q1 is the air flow demand, k2 is a constant, and H is the flight altitude corresponding to the target flight condition.

[0110] For example, the relationship between the air flow demand of the fuel cell system and the altitude when considering the change in oxygen concentration can be obtained based on the initial air flow demand Q0 and the first change relationship: Then, the above calculation formula for calculating the air flow requirement is determined according to the relationship, wherein Q is the air flow requirement of the fuel cell system, and H0 is different flight altitudes.

[0111] Figure 4 This is a schematic diagram of the change in the required air flow of an air compressor with the altitude involved in the embodiment of the present disclosure. According to the third relationship and Figure 4 It can be seen that after considering the change of oxygen concentration with altitude, the air flow demand increases faster with the increase of altitude. The air flow is proportional to the speed of the air compressor. As the altitude increases, the speed of the air compressor needs to increase accordingly to match the greater air flow demand of the fuel cell stack.

[0112] Determine initial air flow requirements by:

[0113] Obtaining a first relationship between an air flow demand of a fuel cell system and an air compressor speed of an air compressor;

[0114] Obtaining a second relationship between the air compressor speed and the flight altitude;

[0115] Determining a third relationship between the air flow requirement of the fuel cell system and the flight altitude based on the first relationship and the second relationship;

[0116] According to the third relationship, the initial air flow requirement is calculated;

[0117] Calculate the initial air flow requirement by using the following calculation:

[0118] Q0=k0k1H

[0119] Among them, Q0 is the initial air flow demand, k0 and k1 are constants, and H is the flight altitude corresponding to the target flight condition.

[0120] For example, the first relationship can be expressed as Q0=k0N0, and the second relationship can be expressed as N0=k1H0. According to the first relationship and the second relationship, the third relationship can be obtained as Q0=k0k1H0, where N0 is the compressor speed of the air compressor, and H0 is different flight altitudes.

[0121] Specifically, the constant values ​​k0 and k1 are related to the specifications of the specific air compressor used. The relationship between the rate of compressed air flow and the air compressor speed of air compressors of different specifications will be different. Since a higher speed can provide more power, the air compressor can compress air faster and output it. Therefore, in general, the air flow of the air compressor is positively correlated with its speed, that is, as the speed increases, the air flow will also increase. The disclosed embodiment does not specifically limit the constant values ​​k0 and k1 and their determination methods.

[0122] In a possible manner, obtaining the first change relationship includes:

[0123] Collect oxygen content corresponding to different flight altitudes;

[0124] Performing curve fitting for different flight altitudes and oxygen contents corresponding to different flight altitudes to obtain a first variation relationship;

[0125] The first change relationship can be expressed by the following exponential relationship:

[0126] O2=O′2*e -k H0

[0127] Among them, O2 is the oxygen content relative to sea level, O2′ is the oxygen content at sea level, k is a constant, and H0 is the flight altitude.

[0128] For example, the oxygen content at different flight altitudes can be collected, and the different flight altitudes and each flight altitude data can be curve fitted. Through fitting, the change of oxygen content with the flight altitude can be approximated as an exponential relationship. Then, based on the exponential relationship and the initial air flow demand, the air flow demand of the air compressor of the fuel cell system under the target flight condition is calculated.

[0129] Figure 5 FIG. 1 is a schematic diagram of the change of oxygen content with altitude involved in the embodiment of the present disclosure. Figure 5 As shown, compared with the relative oxygen content at sea level, the relative oxygen content gradually decreases with increasing altitude.

[0130] Specifically, in addition to changes in altitude, the oxygen content may also have some slight changes in different geographical locations. These changes may be caused by a variety of factors. For example, in cities or industrial areas, the oxygen content may drop slightly due to the presence of air pollutants. Therefore, according to the actual application scenario, the oxygen content at different local altitudes corresponding to the aircraft can be measured, and the constant value k can be determined by curve fitting. The disclosed embodiments do not specifically limit the constant value k and its determination method.

[0131] In a possible manner, according to the air flow demand, determining the required power of the air compressor of the fuel cell system under the target flight condition includes:

[0132] Calculate the required power of the air compressor using the following formula:

[0133] P air1 =Q1P a k3 / η

[0134] Among them, P air1 is the required power of the air compressor, Q1 is the air flow requirement, P a is the working pressure of the air compressor, k3 is a constant, and η is the energy conversion efficiency of the air compressor.

[0135] For example, based on the initial air flow demand Q0, the initial air compressor power demand P of the air compressor can be obtained according to the following calculation formula without considering the change of oxygen concentration: air0 The calculation formula is:

[0136] P air0 =Q0P a k3 / η

[0137] Substituting the initial air flow demand Q0 calculated above into the equation:

[0138] P air0 =k0k1k3P a H / η

[0139] Therefore, when considering the change in oxygen concentration, based on the air flow demand Q1, the initial air compressor power demand P air0 The calculation formula can be obtained:

[0140]

[0141] Among them, if the power unit is kW, the air flow unit is N*m3 / min, and the pressure Pa is bar, then k3 can be 101.325.

[0142] For example, Figure 6 This is a schematic diagram of a variation of the air compressor power of the air compressor involved in the embodiment of the present disclosure, and a schematic diagram of the variation of the air compressor power with the altitude. Figure 6 It can be seen that after considering the change of oxygen concentration with altitude, the power required by the air compressor increases faster as the altitude increases.

[0143] In a possible way, the required power of the fuel cell stack under the target flight condition is calculated based on the required power of the air compressor, including:

[0144] If the target flight condition is a climbing condition, the required power of the first stack of the fuel cell system under the climbing condition is calculated according to the following formula:

[0145] P stack1 =P air1 +P aff

[0146] Among them, P stack1 is the power required by the first stack, P air1 is the required power of the air compressor, P aff The power requirements of other auxiliary components of the fuel cell system;

[0147] If the target flight condition is a high-altitude level flight condition, the required power of the second stack of the fuel cell system under the high-altitude level flight condition is calculated according to the following calculation formula:

[0148] P stack2 =P air1 +P aff -ΔP

[0149] Among them, P stack2 is the power demand of the second stack, and ΔP is the increase in the stack power of the fuel cell system when the air flow rate increases; or

[0150] If the target flight condition is a landing condition, the required power of the third stack of the fuel cell system under the landing condition is calculated according to the following formula:

[0151] P stack3 =P air1 +P aff

[0152] Among them, P stack3 Power is required for the third fuel cell stack.

[0153] For example, according to the above method for calculating the air compressor required power P of the air compressor air1 The calculation formula can be obtained:

[0154]

[0155] Figure 7 FIG. 1 is a schematic diagram of a system power requirement change in different flight conditions involved in an embodiment of the present disclosure. Figure 7 As shown, the flight conditions of the aircraft may include low-altitude level flight conditions, climbing conditions, high-altitude level flight conditions, landing conditions, and low-altitude level flight conditions. When considering the altitude factor, the required power of the fuel cell system increases in the climbing conditions, high-altitude level flight conditions, and landing conditions.

[0156] It is worth noting that after landing from a high altitude to a low altitude, the aircraft enters the level flight process again, that is, when the aircraft is in a low-altitude level flight condition, the fourth stack required power P of the air compressor can be calculated according to the following calculation formula: stack4 :

[0157]

[0158] In a possible way, the required power of the fuel cell stack under the target flight condition is calculated based on the required power of the air compressor, including:

[0159] According to the calculation formula, the improvement value of the fuel cell system stack power is calculated:

[0160] ΔP=P2-P1

[0161] Wherein, P1 is the first required power of the fuel cell system when the flight altitude is not considered, and P2 is the second required power of the fuel cell system when the altitude is considered.

[0162] It should be understood that if the change in oxygen concentration with altitude is taken into account, the stack air flow requirement is greater when flying at high altitudes, and increasing the stack air flow will result in a small increase in stack power.

[0163] Figure 8 Schematic diagram of a stack power variation with load and air flow rate involved in the embodiment of the present disclosure. Figure 8 As shown, this part of the power increase can be calibrated as ΔP, and the value of ΔP can be measured in advance before the aircraft performs a flight operation, which is not limited in the embodiments of the present disclosure.

[0164] Reference Fig. 9 , Fig. 9 This is a structural block diagram of a fuel cell system control device involved in an embodiment of the present disclosure. Based on the same inventive concept as the above embodiment, the device includes:

[0165] An acquisition module 10 is used to acquire flight parameters of the aircraft, wherein the flight parameters include the flight altitude of the aircraft;

[0166] A determination module 20, configured to determine a target flight condition of the aircraft according to the flight parameters;

[0167] A calculation module 30, used to calculate the stack power required by the fuel cell system of the aircraft under the target flight condition;

[0168] The control module 40 is used to control the fuel cell system to provide power support for the aircraft based on the power demand of the fuel cell stack.

[0169] Optionally, the calculation module 30 is used to:

[0170] calculating the air flow demand of the air compressor of the fuel cell system under the target flight condition;

[0171] Determining the required power of the air compressor of the fuel cell system under the target flight condition according to the air flow requirement;

[0172] The required power of the fuel cell stack of the fuel cell system under the target flight condition is calculated based on the required power of the air compressor.

[0173] Optionally, the calculation module 30 is used to:

[0174] If the target flight condition is a climbing condition, the required power of the first stack of the fuel cell system under the climbing condition is calculated according to the following calculation formula:

[0175] P stack1 =P air1 +P aff

[0176] Among them, P stack1 is the power required by the first stack, P air1 is the required power of the air compressor, P aff The power requirements of other auxiliary components of the fuel cell system;

[0177] If the target flight condition is a high-altitude level flight condition, the required power of the second stack of the fuel cell system under the high-altitude level flight condition is calculated according to the following calculation formula:

[0178] P stack2 =P air1 +P aff -ΔP

[0179] Among them, P stack2 is the power demand of the second stack, and ΔP is the increase in the stack power of the fuel cell system when the air flow rate increases; or

[0180] If the target flight condition is a landing condition, the required power of the third stack of the fuel cell system under the landing condition is calculated according to the following calculation formula:

[0181] P stack3 =P air1 +P aff

[0182] Among them, P stack3 Power is required for the third fuel cell stack.

[0183] Optionally, the calculation module 30 is used to:

[0184] According to the calculation formula, the improvement value of the stack power of the fuel cell system is calculated:

[0185] ΔP=P2-P1

[0186] Wherein, P1 is the first required power of the fuel cell system when the flight altitude is not considered, and P2 is the second required power of the fuel cell system when the altitude is considered.

[0187] Optionally, the calculation module 30 is used to:

[0188] The required power of the air compressor is calculated by the following formula:

[0189] P air1 =Q1P a k3 / η

[0190] Among them, P air1 is the required power of the air compressor, Q1 is the air flow requirement, P a is the working pressure of the air compressor, k3 is a constant, and η is the energy conversion efficiency of the air compressor.

[0191] Optionally, the calculation module 30 is used to:

[0192] determining an initial air flow requirement, wherein the initial air flow requirement is an air flow requirement of the fuel cell system under the target flight condition without considering a change in oxygen concentration;

[0193] Acquire a first change relationship, where the first change relationship is used to characterize a change relationship between oxygen content and flight altitude;

[0194] Calculating the air flow demand according to the initial air flow demand and the first change relationship;

[0195] The air flow requirement is calculated according to the following formula:

[0196]

[0197] Wherein, Q1 is the air flow demand, k2 is a constant, and H is the flight altitude corresponding to the target flight condition.

[0198] Optionally, the calculation module 30 is used to:

[0199] Obtaining a first relationship between the air flow demand of the fuel cell system and the air compressor speed of the air compressor;

[0200] Obtaining a second relationship between the air compressor speed and the flight altitude;

[0201] Determining a third relationship between the air flow requirement of the fuel cell system and the flight altitude according to the first relationship and the second relationship;

[0202] Calculating the initial air flow requirement according to the third relationship;

[0203] The initial air flow requirement is calculated by using the following formula:

[0204] Q0=k0k1H

[0205] Wherein, Q0 is the initial air flow requirement, k0 and k1 are both constants, and H is the flight altitude corresponding to the target flight condition.

[0206] Optionally, the calculation module 30 is used to:

[0207] Collect oxygen content corresponding to different flight altitudes;

[0208] Performing curve fitting on the different flight altitudes and the oxygen contents corresponding to the different flight altitudes to obtain the first variation relationship;

[0209] The first change relationship can be expressed by the following exponential relationship:

[0210] O2=O′2*e -k H0

[0211] Among them, O2 is the oxygen content relative to sea level, O2′ is the oxygen content at sea level, k is a constant, and H0 is the flight altitude.

[0212] It should be noted that, since the steps executed by the device of this embodiment are the same as the steps of the aforementioned method embodiment, its specific implementation method and the technical effects that can be achieved can refer to the aforementioned embodiment and will not be repeated here.

[0213] In addition, in one embodiment, an embodiment of the present disclosure further provides an electronic device, which includes a processor, a memory, and a computer program stored in the memory, and the computer program implements the steps of the method in the aforementioned embodiment when executed by the processor.

[0214] In addition, in one embodiment, an embodiment of the present disclosure further provides a computer storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the steps of the method in the aforementioned embodiment are implemented.

[0215] In some embodiments, the computer readable storage medium may be a memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash memory, magnetic surface memory, optical disk, or CD-ROM; or various devices including one or any combination of the above memories. The computer may be various computing devices including intelligent terminals and servers.

[0216] In some embodiments, executable instructions may be in the form of a program, software, software module, script or code, written in any form of programming language (including compiled or interpreted languages, or declarative or procedural languages), and may be deployed in any form, including as a stand-alone program or as a module, component, subroutine or other unit suitable for use in a computing environment.

[0217] As an example, executable instructions may, but do not necessarily, correspond to a file in a file system, may be stored as part of a file that stores other programs or data, such as in one or more scripts in a HyperText Markup Language (HTML) document, in a single file dedicated to the program in question, or in multiple coordinated files (e.g., files storing one or more modules, subroutines, or code portions).

[0218] By way of example, executable instructions may be deployed to be executed on one computing device, or on multiple computing devices located at one site, or on multiple computing devices distributed across multiple sites and interconnected by a communication network.

[0219] It should be noted that, in this article, the terms "include", "may include" or any other variations thereof are intended to cover non-exclusive inclusions, so that a process, method, article or system including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or system. In the absence of further restrictions, an element defined by the sentence "includes a ..." does not exclude the existence of other identical elements in the process, method, article or system including the element.

[0220] The serial numbers of the above-mentioned embodiments of the present disclosure are only for description and do not represent the advantages or disadvantages of the embodiments.

[0221] Through the description of the above implementation methods, those skilled in the art can clearly understand that the above-mentioned embodiment methods can be implemented by means of software plus a necessary general hardware platform, and of course by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present disclosure, or the part that contributes to the prior art, can be embodied in the form of a software product, which is stored in a storage medium (such as a read-only memory / random access memory, a magnetic disk, or an optical disk), and includes a number of instructions for enabling a multimedia terminal device (which can be a mobile phone, a computer, a television receiver, or a network device, etc.) to execute the methods described in each embodiment of the present disclosure.

[0222] The above descriptions are only optional embodiments of the present disclosure, and are not intended to limit the patent scope of the present disclosure. All equivalent structural transformations made using the contents of the present disclosure and the drawings under the inventive concept of the present disclosure, or direct / indirect applications in other related technical fields are included in the patent protection scope of the present disclosure.

Claims

1. A fuel cell system control method, characterized in that: include: Acquiring flight parameters of an aircraft, wherein the flight parameters include a flight altitude of the aircraft; Determining a target flight condition of the aircraft according to the flight parameters; Calculating the required power of the fuel cell stack of the fuel cell system of the aircraft under the target flight condition; Based on the power demand of the fuel cell stack, the fuel cell system is controlled to provide power support for the aircraft.

2. The method according to claim 1, characterized in that The calculating the stack power requirement of the fuel cell system of the aircraft under the target flight condition includes: calculating the air flow demand of the air compressor of the fuel cell system under the target flight condition; Determining the required power of the air compressor of the fuel cell system under the target flight condition according to the air flow requirement; The required power of the fuel cell stack of the fuel cell system under the target flight condition is calculated based on the required power of the air compressor.

3. The method according to claim 2, characterized in that The step of calculating the required power of the fuel cell stack of the fuel cell system under the target flight condition according to the required power of the air compressor includes: If the target flight condition is a climbing condition, the required power of the first stack of the fuel cell system under the climbing condition is calculated according to the following calculation formula: P stack1 =P air1 +P aff Among them, P stack1 is the power required by the first battery stack, P air1 is the required power of the air compressor, P aff The power requirements of other auxiliary components of the fuel cell system; If the target flight condition is a high-altitude level flight condition, the required power of the second stack of the fuel cell system under the high-altitude level flight condition is calculated according to the following calculation formula: P stack2 =P air1 +P aff -ΔP Among them, P stack2 is the power demand of the second stack, and ΔP is the increase in the stack power of the fuel cell system when the air flow rate increases; or If the target flight condition is a landing condition, the required power of the third stack of the fuel cell system under the landing condition is calculated according to the following calculation formula: P stack3 =P air1 +P aff Among them, P stack3 Power is required for the third fuel cell stack.

4. The method according to claim 2, characterized in that: The step of calculating the required power of the fuel cell stack of the fuel cell system under the target flight condition according to the required power of the air compressor includes: According to the calculation formula, the improvement value of the stack power of the fuel cell system is calculated: ΔP=P2-P1 Wherein, P1 is the first required power of the fuel cell system when the flight altitude is not considered, and P2 is the second required power of the fuel cell system when the altitude is considered.

5. The method according to claim 2, characterized in that: The step of determining the required power of the air compressor of the fuel cell system under the target flight condition according to the air flow requirement includes: The required power of the air compressor is calculated by the following formula: P air1 =Q1P a k3 / η Among them, P air1 is the required power of the air compressor, Q1 is the air flow requirement, P a is the working pressure of the air compressor, k3 is a constant, and η is the energy conversion efficiency of the air compressor.

6. The method according to claim 2, characterized in that The calculating the air flow demand of the air compressor of the fuel cell system under the target flight condition includes: determining an initial air flow requirement, wherein the initial air flow requirement is an air flow requirement of the fuel cell system under the target flight condition without considering a change in oxygen concentration; Acquire a first change relationship, where the first change relationship is used to characterize a change relationship between oxygen content and flight altitude; Calculating the air flow demand according to the initial air flow demand and the first change relationship; The air flow requirement is calculated according to the following formula: Wherein, Q1 is the air flow demand, k2 is a constant, and H is the flight altitude corresponding to the target flight condition.

7. The method according to claim 6, characterized in that The determining of the initial air flow requirement comprises: Obtaining a first relationship between the air flow demand of the fuel cell system and the air compressor speed of the air compressor; Obtaining a second relationship between the air compressor speed and the flight altitude; Determining a third relationship between the air flow requirement of the fuel cell system and the flight altitude according to the first relationship and the second relationship; Calculating the initial air flow requirement according to the third relationship; The initial air flow requirement is calculated by using the following formula: Q0=k0k1H Wherein, Q0 is the initial air flow requirement, k0 and k1 are both constants, and H is the flight altitude corresponding to the target flight condition.

8. The method according to claim 6, characterized in that The obtaining of the first change relationship includes: Collect oxygen content corresponding to different flight altitudes; Performing curve fitting on the different flight altitudes and the oxygen contents corresponding to the different flight altitudes to obtain the first variation relationship; The first change relationship can be expressed by the following exponential relationship: O2=O′2*e -k H0 Among them, O2 is the oxygen content relative to sea level, O′2 is the oxygen content at sea level, k is a constant, and H0 is the flight altitude.

9. A fuel cell system control device, characterized in that: include: An acquisition module, used to acquire flight parameters of the aircraft, wherein the flight parameters include the flight altitude of the aircraft; A determination module, used to determine a target flight condition of the aircraft according to the flight parameters; A calculation module is used to calculate the stack power requirement of the fuel cell system of the aircraft under the target flight condition; and a control module is used to control the fuel cell system to provide power support for the aircraft based on the stack power requirement.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and the processor executes the computer program to implement the method according to any one of claims 1 to 8.

11. An electronic device, characterized in that: The electronic device comprises a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the method according to any one of claims 1 to 8.

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